EP1818615A1 - Annular combustion chamber of a turbomachine - Google Patents

Annular combustion chamber of a turbomachine Download PDF

Info

Publication number
EP1818615A1
EP1818615A1 EP07101934A EP07101934A EP1818615A1 EP 1818615 A1 EP1818615 A1 EP 1818615A1 EP 07101934 A EP07101934 A EP 07101934A EP 07101934 A EP07101934 A EP 07101934A EP 1818615 A1 EP1818615 A1 EP 1818615A1
Authority
EP
European Patent Office
Prior art keywords
sector
combustion chamber
walls
sectors
chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07101934A
Other languages
German (de)
French (fr)
Other versions
EP1818615B1 (en
Inventor
Mario De Sousa
Didier Hernandez
Thomas Noel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1818615A1 publication Critical patent/EP1818615A1/en
Application granted granted Critical
Publication of EP1818615B1 publication Critical patent/EP1818615B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an annular combustion chamber of a turbomachine, of the type comprising an inner wall, an outer wall and a chamber bottom disposed between said walls in the upstream region of said chamber.
  • a turbomachine of the type comprising an inner wall, an outer wall and a chamber bottom disposed between said walls in the upstream region of said chamber.
  • two attachment flanges disposed downstream of the chamber bottom allow to hang said walls to other parts of the turbomachine, often internal and external casings surrounding the combustion chamber.
  • said inner and outer walls of the chamber were made of metal or metal alloy and it was necessary to cool these walls so that they can withstand the temperatures reached during operation of the turbomachine.
  • Ceramic materials are more resistant to high temperatures and have a lower density than the metals generally used.
  • the gains made in cooling air and in mass make it possible to improve the efficiency of the turbomachine.
  • the ceramic materials used are preferably ceramic matrix composite materials, commonly referred to as CMCs, chosen for their good mechanical properties and their ability to retain these properties at high temperatures.
  • this part is preferably made of metal or metal alloy, rather than ceramic material, in order to be able to use known and tested fastening methods to date, such as welding, to fix on this chamber bottom, other parts (usually fuel injection systems and baffles).
  • the ceramic materials used to make the walls often have a coefficient of expansion about three times less than that of the metallic materials used to make the chamber bottom, so that the inner and outer walls expand and shrink less than the bottom. of chamber, during variations in operating temperature of the chamber.
  • the variations in variation between the inside and outside diameters of the bottom of the chamber and the diameters of the walls generate stresses in these parts, during the operation of the bedroom. These stresses can be at the origin of cracks in the walls, the ceramic materials being, by nature, quite fragile.
  • a solution described in the document FR 2,855,249 consists in providing a plurality of flexible fastening tabs connecting the chamber bottom (made in one annular piece) audits walls, these tabs being able to deform elastically depending on the expansion gaps between the parts.
  • the main disadvantage of such a structure lies in the poor dynamic behavior, during the operation of the turbomachine, the flexible fastening tabs and it is often necessary to provide damping systems to limit the deformation of these legs and the vibrations generated.
  • there remain spaces between the fastening tabs through which fresh air rushes into the combustion chamber, which can degrade the efficiency of the latter by promoting the formation of pollutant emissions, such as, for example , unburned and / or carbon monoxide.
  • the invention aims to remedy these drawbacks, or at least to mitigate them, and aims to propose a combustion chamber having an alternative structure to the structure with flexible fastening tabs described in FIG. FR 2,855,249 , which is able to adapt to the expansion gaps between the chamber floor and the outer and inner walls.
  • the invention relates to an annular combustion chamber of the aforementioned type, characterized in that said chamber bottom is divided into several adjacent sectors, each sector being attached to said walls.
  • the side edges of the chamber bottom sectors move relative to each other according to the operating temperature variations of the chamber: during a rise in temperature, each sector expands and the lateral edges of the sectors are approaching. from each other, while during a decrease in temperature, the lateral edges of the sectors deviate from each other.
  • the inner and outer diameters of the chamber bottom vary less than if the chamber bottom was in one annular piece, which generates less stress between the bottom and the walls of the chamber.
  • the lateral edges of the sectors are as close as possible.
  • they are in contact so as to significantly limit, if not prevent, the passage of fresh air between them, from outside to inside the chamber.
  • each sector has lateral edges such that the lateral edges of two neighboring sectors overlap. This makes it possible to obtain a good seal between sectors. When the sectors deviate (or move closer) from each other, said lateral edges slide on one another and the sealing between sectors is maintained.
  • each sector comprises a lip extending along one of its lateral edges, this lip being protruding with respect to one of the faces (upstream or downstream) of this sector and covering the lateral edge. from the neighboring sector.
  • the invention is particularly interesting when the chamber bottom is made of metal or metal alloy while the inner and outer walls are made of ceramic materials and, in particular, CMC.
  • the invention can be applied in other cases, for example with a bottom chamber and walls of metal materials, or with a chamber bottom and walls of ceramic materials.
  • the fact of sectoring the chamber bottom makes it possible to promote the assembly of the bottom walls.
  • the sectors are more flexible than a monoblock annular chamber bottom, there is less stress between these parts during their assembly. This assembly is carried out, for example, by bolting. This reduces the risk of these parts breaking at their attachment points.
  • turbojet turbojet
  • turboprop gas turbine land
  • the chamber bottom 30 is made of metal alloy, while the walls 26 and 28 of the chamber 24 are made of ceramic matrix composite material, or CMC.
  • the chamber bottom 30 is divided into several adjacent sectors 130.
  • Each sector 130 has a central portion 133, oriented rather perpendicular to the axis 10, and in which is formed at least one through hole 40.
  • This central portion 133 extends at the bottom and at the top by two flaps 132, 134, oriented instead along the axis 10, and respectively attached to the inner and outer walls 26 and 28.
  • Each sector 130 includes a lip 60 extending along one of its side edges 130a, preferably over substantially the entire length of the central portion 133 thereof.
  • the other side edge of the sector is devoid of lip and will be hereinafter called simple edge 130b.
  • the lip 60 protrudes from the central portion of the sector 130, upstream or downstream, so as to cover the single edge 130b of the neighboring sector.
  • the lip 60 is projecting from the side of the upstream face of the sector 130 which allows, if necessary, to mount a deflector 23 on the downstream face thereof.
  • the lip 60 may be made directly during the manufacture of the sector 130, or during a subsequent machining step in its manufacture.
  • the lip 60 may also consist of an added band, for example by welding (brazing), on the lateral edge 130a of the sector.
  • the edge lateral 130a and the lip 60 of a sector deviate from the single lateral edge 130b of the neighboring sector.
  • the lip 60 is chosen to be wide enough to prevent the creation of an excessive inter-sector circumferential clearance when the sectors 130 are spaced apart. When the lip 60 is wide enough for the circumferential clearance between sectors 130 to remain zero or negative, it prevents (or at least significantly limits) the passage of fresh air between the sectors 130.
  • each wall sector 130 is attached to at least one of the walls 26, 28 at two attachment points 36, 36 ', so as to ensure good fixing. This also makes it possible to prevent the sector 130 from pivoting relative to this wall, around one of its attachment points 36, 36 '.
  • each sector 130 is attached to each of the walls 26, 28 at two points of attachment 36 and 36 '.
  • a fastening system is used which allows the approximation or spacing (in the circumferential direction of the chamber bottom) of said two attachment points 36 and 36 '. In this way the creation of stresses in the wall in question is avoided, when the attachment points 36 and 36 'deviate (or come closer) from one another because of the expansion (or retraction). sector 130.
  • Such an attachment system corresponds, for example, to a bolt 52 cooperating with at least one oblong hole 50 whose width corresponds substantially to the diameter of the screw of the bolt 52.
  • This oblong hole 50 may be formed in a flap 132 (134). ) of the chamber bottom sector 130, in a wall 26 (28) or in these two parts at a time. In the example, it was chosen to make an oblong hole 50 only in the flaps 132, 134.
  • the holes made in the walls 26, 29, are all cylindrical, of diameter corresponding to that of the screws of the bolts 52 used.
  • Each oblong hole 50 is circumferentially oriented (ie, the length of each hole is oriented along the circumference of the annular chamber bottom) and the bolt 52 cooperating with this hole 50 can thus move circumferentially within the hole 50 as shown by the double arrow B.
  • all bolts 52 are not shown.
  • the sectors 130 of the chamber bottom 30 being made of metal material, generally made of refractory metal alloy, it is easy to fix on them, for example by welding (soldering), the various elements of an injection system. fuel 20, as a holding system 19 and a mixer 21. Furthermore, if necessary, it is also possible to fix on the downstream wall of each sector 130 a baffle 23 for protecting the sector 130 of the high temperature gases of the combustion chamber. Such a deflector 23 is optional and its presence depends mainly on the high temperature resistance of the material used to produce the segments 130.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The combustion chamber, having inner (26) and outer (28) walls of a ceramic material, and a metal or alloy base between them on the upstream side, has the base divided into a series of sectors (130), each attached to the inner and outer walls and having overlapping adjacent lateral edges (130a, 130b), formed by projecting lips (60) on at least one edge, normally along the whole length of the middle section of each sector. Each of the base sectors is also attached to at least the inner or outer wall at two or more points (36, 36'), one of which has an oblong slot to allow for adjustment.

Description

L'invention concerne une chambre de combustion annulaire d'une turbomachine, du type comprenant une paroi interne, une paroi externe et un fond de chambre disposé entre lesdites parois dans la région amont de ladite chambre. Généralement, deux brides d'accrochage disposées en aval du fond de chambre permettent d'accrocher lesdites parois à d'autres parties de la turbomachine, souvent des carters interne et externe entourant la chambre de combustion.The invention relates to an annular combustion chamber of a turbomachine, of the type comprising an inner wall, an outer wall and a chamber bottom disposed between said walls in the upstream region of said chamber. Generally, two attachment flanges disposed downstream of the chamber bottom allow to hang said walls to other parts of the turbomachine, often internal and external casings surrounding the combustion chamber.

Auparavant, lesdites parois interne et externe de la chambre étaient en métal ou en alliage métallique et il était nécessaire de refroidir ces parois pour qu'elles puissent supporter les températures atteintes lors du fonctionnement de la turbomachine.Previously, said inner and outer walls of the chamber were made of metal or metal alloy and it was necessary to cool these walls so that they can withstand the temperatures reached during operation of the turbomachine.

Aujourd'hui, pour diminuer le débit d'air alloué au refroidissement de ces parois, on réalise celles-ci en matériau céramique plutôt qu'en métal. En effet, les matériaux céramiques résistent mieux aux hautes températures et possèdent une masse volumique plus faible que les métaux généralement utilisés. Les gains réalisés en air de refroidissement et en masse permettent d'améliorer le rendement de la turbomachine. Les matériaux céramiques utilisés sont, de préférence, des matériaux composites à matrice céramique, communément appelés CMC, choisis pour leurs bonnes propriétés mécaniques et leur capacité à conserver ces propriétés à hautes températures.Today, to reduce the air flow allocated to the cooling of these walls, they are made of ceramic material rather than metal. In fact, ceramic materials are more resistant to high temperatures and have a lower density than the metals generally used. The gains made in cooling air and in mass make it possible to improve the efficiency of the turbomachine. The ceramic materials used are preferably ceramic matrix composite materials, commonly referred to as CMCs, chosen for their good mechanical properties and their ability to retain these properties at high temperatures.

En ce qui concerne le fond de chambre, on réalise, de préférence, cette partie en métal ou en alliage métallique, plutôt qu'en matériau céramique, afin de pouvoir utiliser des méthodes de fixation connues et éprouvées à ce jour, comme le soudage, permettant de fixer sur ce fond de chambre, d'autres pièces (généralement des systèmes d'injection de carburant et des déflecteurs).With regard to the chamber base, this part is preferably made of metal or metal alloy, rather than ceramic material, in order to be able to use known and tested fastening methods to date, such as welding, to fix on this chamber bottom, other parts (usually fuel injection systems and baffles).

Or, les matériaux céramiques utilisés pour réaliser les parois présentent souvent un coefficient de dilatation environ trois fois inférieur à celui des matériaux métalliques utilisés pour réaliser le fond de chambre, de sorte que les parois interne et externe se dilatent et se rétractent moins que le fond de chambre, lors des variations de température de fonctionnement de la chambre. En d'autres termes, les écarts de variation entre les diamètres intérieur et extérieur du fond de chambre et les diamètres des parois, génèrent des contraintes dans ces pièces, lors du fonctionnement de la chambre. Ces contraintes peuvent être à l'origine de fissurations dans les parois, les matériaux céramiques étant, par nature, assez fragiles.However, the ceramic materials used to make the walls often have a coefficient of expansion about three times less than that of the metallic materials used to make the chamber bottom, so that the inner and outer walls expand and shrink less than the bottom. of chamber, during variations in operating temperature of the chamber. In other words, the variations in variation between the inside and outside diameters of the bottom of the chamber and the diameters of the walls, generate stresses in these parts, during the operation of the bedroom. These stresses can be at the origin of cracks in the walls, the ceramic materials being, by nature, quite fragile.

Pour résoudre ce problème, une solution décrite dans le document FR 2 855 249 , consiste à prévoir une pluralité de pattes de fixation souples reliant le fond de chambre (réalisé en une seule pièce annulaire) audites parois, ces pattes étant capables de se déformer élastiquement en fonction des écarts de dilatation entre les pièces. L'inconvénient principal d'une telle structure réside dans le mauvais comportement dynamique, lors du fonctionnement de la turbomachine, des pattes de fixation souples et, il est souvent nécessaire de prévoir des systèmes d'amortissement pour limiter la déformation de ces pattes et les vibrations engendrées. En outre, il subsiste entre les pattes de fixation, des espaces par lesquels l'air frais s'engouffre dans la chambre de combustion, ce qui peut dégrader le rendement de celle-ci en favorisant la formation d'émissions polluantes comme, par exemple, des imbrûlés et/ou du monoxyde de carbone.To solve this problem, a solution described in the document FR 2,855,249 , consists in providing a plurality of flexible fastening tabs connecting the chamber bottom (made in one annular piece) audits walls, these tabs being able to deform elastically depending on the expansion gaps between the parts. The main disadvantage of such a structure lies in the poor dynamic behavior, during the operation of the turbomachine, the flexible fastening tabs and it is often necessary to provide damping systems to limit the deformation of these legs and the vibrations generated. In addition, there remain spaces between the fastening tabs through which fresh air rushes into the combustion chamber, which can degrade the efficiency of the latter by promoting the formation of pollutant emissions, such as, for example , unburned and / or carbon monoxide.

L'invention vise à remédier à ces inconvénients, ou tout au moins à les atténuer, et a pour but de proposer une chambre de combustion présentant une structure alternative à la structure à pattes de fixation souples décrite dans FR 2 855 249 , qui soit capable de s'adapter aux écarts de dilatation entre le fond de chambre et les parois externe et interne.The invention aims to remedy these drawbacks, or at least to mitigate them, and aims to propose a combustion chamber having an alternative structure to the structure with flexible fastening tabs described in FIG. FR 2,855,249 , which is able to adapt to the expansion gaps between the chamber floor and the outer and inner walls.

Pour atteindre ce but, l'invention a pour objet une chambre de combustion annulaire du type précité, caractérisée en ce que ledit fond de chambre est divisé en plusieurs secteurs voisins, chaque secteur étant attaché auxdites parois.To achieve this object, the invention relates to an annular combustion chamber of the aforementioned type, characterized in that said chamber bottom is divided into several adjacent sectors, each sector being attached to said walls.

Ainsi, les bords latéraux des secteurs du fond de chambre se déplacent les uns par rapport aux autres suivant les variations de température de fonctionnement de la chambre : lors d'une montée en température, chaque secteur se dilate et les bords latéraux des secteurs se rapprochent les uns des autres, tandis que lors d'une diminution de la température, les bords latéraux des secteurs s'écartent les uns des autres. De cette façon, lorsque la température varie, les diamètres intérieur et extérieur du fond de chambre varient moins que si le fond de chambre était en une seule pièce annulaire, ce qui génère moins de contraintes entre ce fond et les parois de la chambre.Thus, the side edges of the chamber bottom sectors move relative to each other according to the operating temperature variations of the chamber: during a rise in temperature, each sector expands and the lateral edges of the sectors are approaching. from each other, while during a decrease in temperature, the lateral edges of the sectors deviate from each other. In this way, when the temperature varies, the inner and outer diameters of the chamber bottom vary less than if the chamber bottom was in one annular piece, which generates less stress between the bottom and the walls of the chamber.

A la température maximum de fonctionnement de la chambre, les bords latéraux des secteurs sont les plus rapprochés possible. Avantageusement, ils sont en contact de manière à limiter significativement, voire empêcher, le passage d'air frais entre eux, de l'extérieur vers l'intérieur de la chambre.At the maximum operating temperature of the chamber, the lateral edges of the sectors are as close as possible. Advantageously, they are in contact so as to significantly limit, if not prevent, the passage of fresh air between them, from outside to inside the chamber.

Avantageusement, les secteurs présentent des bords latéraux tels que les bords latéraux de deux secteurs voisins se chevauchent. Ceci permet d'obtenir une bonne étanchéité entre secteurs. Lorsque les secteurs s'écartent (ou se rapprochent) les uns des autres, lesdits bords latéraux glissent l'un sur l'autre et l'étanchéité entre secteurs est maintenue. Selon un mode de réalisation, chaque secteur comprend une lèvre s'étendant le long d'un de ses bords latéraux, cette lèvre étant en saillie par rapport à l'une des faces (amont ou aval) de ce secteur et recouvrant le bord latéral du secteur voisin.Advantageously, the sectors have lateral edges such that the lateral edges of two neighboring sectors overlap. This makes it possible to obtain a good seal between sectors. When the sectors deviate (or move closer) from each other, said lateral edges slide on one another and the sealing between sectors is maintained. According to one embodiment, each sector comprises a lip extending along one of its lateral edges, this lip being protruding with respect to one of the faces (upstream or downstream) of this sector and covering the lateral edge. from the neighboring sector.

Comme expliqué plus haut, l'invention est particulièrement intéressante lorsque le fond de chambre est réalisé en métal ou en alliage métallique tandis que les parois intérieure et extérieure sont en matériaux céramiques et, notamment, en CMC. Toutefois, l'invention peut s'appliquer dans d'autres cas, par exemple avec un fond de chambre et des parois en matériaux métalliques, ou encore avec un fond de chambre et des parois en matériaux céramiques. Dans ces derniers exemples, où les problèmes liés aux écarts de dilatation entre les parois et le fond de chambre sont moins importants, voire inexistants, le fait de sectoriser le fond de chambre permet de favoriser l'assemblage du fond aux parois. En particulier, comme les secteurs sont plus souples qu'un fond de chambre annulaire monobloc, il se crée moins de contraintes entre ces pièces lors de leur assemblage. Cet assemblage est réalisé, par exemple, par boulonnage. On diminue ainsi le risque de voir ces pièces se casser au niveau de leurs points d'attache.As explained above, the invention is particularly interesting when the chamber bottom is made of metal or metal alloy while the inner and outer walls are made of ceramic materials and, in particular, CMC. However, the invention can be applied in other cases, for example with a bottom chamber and walls of metal materials, or with a chamber bottom and walls of ceramic materials. In these latter examples, where the problems related to the expansion gaps between the walls and the chamber bottom are less important, or nonexistent, the fact of sectoring the chamber bottom makes it possible to promote the assembly of the bottom walls. In particular, since the sectors are more flexible than a monoblock annular chamber bottom, there is less stress between these parts during their assembly. This assembly is carried out, for example, by bolting. This reduces the risk of these parts breaking at their attachment points.

L'invention et ses avantages seront bien compris à la lecture de la description détaillée qui suit, d'un exemple de chambre de combustion selon l'invention, donné à titre illustratif et non limitatif. Cette description se réfère aux planches de dessins annexées sur lesquelles :

  • la figure 1 est une vue schématique, en demi-section axiale, d'une partie de turbomachine équipée d'une chambre de combustion selon l'invention ;
  • la figure 2 est une vue en perspective partielle, vue de l'amont, du fond de la chambre de combustion de la figure 1 ;
  • la figure 3 est une vue de détail, en perspective, de deux secteurs du fond de chambre de la figure 2, vus de l'amont ;
  • la figure 4 est une vue de détail, en perspective, d'un secteur du fond de chambre de la figure 2, vu de l'aval ;
The invention and its advantages will be better understood on reading the following detailed description of an example of a combustion chamber according to the invention, given as an illustration and not as a limitation. This description refers to the attached drawing plates in which:
  • FIG. 1 is a diagrammatic view, in axial half-section, of a turbomachine portion equipped with a combustion chamber according to the invention;
  • Figure 2 is a partial perspective view, seen from upstream, of the bottom of the combustion chamber of Figure 1;
  • Figure 3 is a detail view, in perspective, of two sectors of the chamber bottom of Figure 2, seen from upstream;
  • Figure 4 is a detail view, in perspective, of a sector of the chamber bottom of Figure 2, seen from the downstream;

L'invention se destine à tout type de turbomachine : turboréacteur, turbopropulseur, turbine à gaz terrestre... Dans l'exemple qui suit, on s'intéresse plus particulièrement à un turboréacteur d'avion.The invention is intended for any type of turbomachine: turbojet, turboprop, gas turbine land ... In the following example, it is more particularly interested in an aircraft turbojet engine.

La figure 1 montre en demi-section axiale une partie de turboréacteur comprenant :

  • une enveloppe circulaire interne ou carter interne 12, d'axe principal 10 correspondant à l'axe de rotation du turboréacteur ;
  • une enveloppe circulaire externe ou carter externe 14, coaxial au carter interne 12 ;
  • un espace annulaire 16 compris entre les deux carters 12 et 14 recevant le comburant comprimé, généralement de l'air, provenant en amont d'un compresseur (non représenté) du turboréacteur, au travers d'un conduit annulaire de diffusion 18.
FIG. 1 shows in axial half-section a turbojet part comprising:
  • an inner circular casing or internal casing 12, of main axis 10 corresponding to the axis of rotation of the turbojet engine;
  • an outer circular casing or outer casing 14, coaxial with the inner casing 12;
  • an annular space 16 between the two housings 12 and 14 receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbojet, through an annular diffusion duct 18.

L'espace 16 comporte de l'amont vers l'aval, l'amont et l'aval étant définis par rapport au sens d'écoulement normal des gaz à l'intérieur du turboréacteur, indiqué par les flèches F :

  • un ensemble d'injection pour injecter du carburant dans la chambre de combustion 24 décrite ci-après, cet ensemble d'injection étant formé d'une pluralité de systèmes d'injection 20 régulièrement répartis en amont de la chambre 24 et comportant chacun une buse d'injection de carburant 22 fixée sur le carter extérieur 14. Cette buse d'injection 22 est reliée à la chambre 24 par l'intermédiaire d'un système de maintien 19 et d'un mélangeur 21. Dans un souci de simplification, ces dernières pièces n'ont pas été représentées sur la figure 1, mais elles apparaissent sur les figures 2 à 4 ;
  • une chambre de combustion 24 comprenant une paroi circulaire 26 radialement interne et une paroi circulaire 28 radialement externe, toutes deux coaxiales d'axe 10, et une paroi transversale qui constitue le fond 30 de cette chambre et qui est attachée aux extrémités amont des parois 26, 28. Ce fond de chambre 30 est pourvu d'orifices de passage 40 pour permettre l'injection du carburant, via les buses 22, et d'une partie du comburant, via le mélangeur 21, dans la chambre de combustion ;
  • des brides d'accrochage interne 27 et externe 29, reliant respectivement les parois interne 26 et externe 28 aux carters interne 12 et externe 14 ; et
  • un distributeur annulaire 42 en alliage métallique formant un étage d'entrée de turbine haute pression (non représentée) et comportant classiquement une pluralité d'aubes fixes 44 montées entre une plate-forme circulaire interne 46 et une plate-forme circulaire externe 48. Le distributeur 42 étant fixé aux carters 12 et 14 de la turbomachine par des moyens de fixation appropriés.
The space 16 comprises from upstream to downstream, the upstream and the downstream being defined with respect to the normal flow direction of the gases inside the turbojet, indicated by the arrows F:
  • an injection assembly for injecting fuel into the combustion chamber 24 described below, this injection assembly being formed of a plurality of injection systems 20 regularly distributed upstream of the chamber 24 and each having a nozzle fuel injection 22 fixed on the outer casing 14. This injection nozzle 22 is connected to the chamber 24 via a holding system 19 and a mixer 21. For the sake of simplicity, these last pieces have not been shown in Figure 1, but they appear in Figures 2 to 4;
  • a combustion chamber 24 comprising a circular wall 26 radially inner and a circular wall 28 radially external, both coaxial axis 10, and a transverse wall which constitutes the bottom 30 of this chamber and which is attached to the upstream ends of the walls 26 , 28. This chamber bottom 30 is provided with through-holes 40 to allow fuel injection, via the nozzles 22, and a portion of the oxidant, via the mixer 21, into the combustion chamber;
  • internal and external fastening flanges 29, respectively connecting the inner and outer walls 26 and 26 to the inner and outer casings 12; and
  • an annular metal alloy distributor 42 forming a high pressure turbine inlet stage (not shown) and conventionally comprising a plurality of stationary vanes 44 mounted between an inner circular platform 46 and an outer circular platform 48. distributor 42 being fixed to the casings 12 and 14 of the turbomachine by appropriate fastening means.

Le fond de chambre 30 est réalisé en alliage métallique, tandis que les parois 26 et 28 de la chambre 24 sont en matériau composite à matrice céramique, ou CMC.The chamber bottom 30 is made of metal alloy, while the walls 26 and 28 of the chamber 24 are made of ceramic matrix composite material, or CMC.

Le fond de chambre 30 est divisé en plusieurs secteurs voisins 130. Chaque secteur 130 présente une partie centrale 133, orientée plutôt perpendiculairement à l'axe 10, et dans laquelle est ménagée au moins un orifice de passage 40. Cette partie centrale 133 se prolonge en bas et en haut par deux rabats 132, 134, orientés plutôt suivant l'axe 10, et attachés respectivement aux parois interne 26 et externe 28.The chamber bottom 30 is divided into several adjacent sectors 130. Each sector 130 has a central portion 133, oriented rather perpendicular to the axis 10, and in which is formed at least one through hole 40. This central portion 133 extends at the bottom and at the top by two flaps 132, 134, oriented instead along the axis 10, and respectively attached to the inner and outer walls 26 and 28.

En référence à la figure 2, on va décrire la manière particulière dont les bords latéraux 130a, 130b de deux secteurs voisins 130 se chevauchent. Chaque secteur 130 comprend une lèvre 60 s'étendant le long d'un de ses bords latéraux 130a, de préférence, sur sensiblement toute la longueur de la partie centrale 133 de celui-ci. L'autre bord latéral du secteur est dépourvu de lèvre et sera dénommé ci-après bord simple 130b.Referring to Figure 2, we will describe the particular manner in which the side edges 130a, 130b of two neighboring sectors 130 overlap. Each sector 130 includes a lip 60 extending along one of its side edges 130a, preferably over substantially the entire length of the central portion 133 thereof. The other side edge of the sector is devoid of lip and will be hereinafter called simple edge 130b.

La lèvre 60 est en saillie par rapport à la partie centrale du secteur 130, vers l'amont ou aval, de manière à pouvoir recouvrir le bord simple 130b du secteur voisin. Dans l'exemple représenté sur la figure 4, la lèvre 60 est en saillie du côté de la face amont du secteur 130 ce qui permet, si nécessaire, de monter un déflecteur 23 sur la face aval de celui-ci.The lip 60 protrudes from the central portion of the sector 130, upstream or downstream, so as to cover the single edge 130b of the neighboring sector. In the example shown in Figure 4, the lip 60 is projecting from the side of the upstream face of the sector 130 which allows, if necessary, to mount a deflector 23 on the downstream face thereof.

La lèvre 60 peut être réalisée directement lors de la fabrication du secteur 130, ou lors d'une étape d'usinage ultérieure à sa fabrication. La lèvre 60 peut également consister en une bande rapportée, par exemple par soudage (par brasage), sur le bord latéral 130a du secteur.The lip 60 may be made directly during the manufacture of the sector 130, or during a subsequent machining step in its manufacture. The lip 60 may also consist of an added band, for example by welding (brazing), on the lateral edge 130a of the sector.

Lorsque les secteurs 130 s'écartent les uns des autres, suite à la diminution de la température de fonctionnement de la chambre 24, le bord latéral 130a et la lèvre 60 d'un secteur s'écartent du bord latéral simple 130b du secteur voisin. La lèvre 60 est choisie suffisamment large pour éviter qu'il se crée, lors de l'écartement des secteurs 130, un jeu circonférentiel inter-secteur trop important. Lorsque la lèvre 60 est suffisamment large pour que le jeu circonférentiel entre secteurs 130 reste nul ou négatif, on empêche (ou tout au moins on limite significativement) le passage d'air frais entre les secteurs 130.When the sectors 130 deviate from each other, following the decrease in the operating temperature of the chamber 24, the edge lateral 130a and the lip 60 of a sector deviate from the single lateral edge 130b of the neighboring sector. The lip 60 is chosen to be wide enough to prevent the creation of an excessive inter-sector circumferential clearance when the sectors 130 are spaced apart. When the lip 60 is wide enough for the circumferential clearance between sectors 130 to remain zero or negative, it prevents (or at least significantly limits) the passage of fresh air between the sectors 130.

Toujours de façon à limiter, le passage d'air frais entre les secteurs, on fait en sorte que la face aval (ou amont) de la lèvre 60 soit au contact de la face amont (ou aval) du bord latéral simple 130b adjacent. Toutefois, si les frottements qui accompagnent ce contact sont trop importants et nuisent au déplacement relatif des secteurs 130, on peut laisser subsister un léger jeu axial entre ces faces, au détriment de l'étanchéité entre secteurs 130.Always so as to limit the passage of fresh air between the sectors, it is made that the downstream face (or upstream) of the lip 60 is in contact with the upstream face (or downstream) of the single lateral edge 130b adjacent. However, if the friction which accompanies this contact is too great and adversely affects the relative displacement of the sectors 130, a slight axial clearance can be left between these faces, to the detriment of the sealing between sectors 130.

Selon un autre aspect de l'invention, chaque secteur de paroi 130 est attaché à au moins une des parois 26, 28 en deux points d'attache 36, 36', de manière à garantir une bonne fixation. Ceci permet également d'empêcher le secteur 130 de pivoter par rapport à cette paroi, autour d'un de ses points d'attache 36, 36'. Dans l'exemple, chaque secteur 130 est attaché à chacune des parois 26, 28, en deux points d'attache 36 et 36'.According to another aspect of the invention, each wall sector 130 is attached to at least one of the walls 26, 28 at two attachment points 36, 36 ', so as to ensure good fixing. This also makes it possible to prevent the sector 130 from pivoting relative to this wall, around one of its attachment points 36, 36 '. In the example, each sector 130 is attached to each of the walls 26, 28 at two points of attachment 36 and 36 '.

Avantageusement, pour attacher le secteur 130 aux parois 26, 28, on utilise un système d'attache qui autorise le rapprochement ou l'écartement (selon la direction circonférentielle du fond de chambre) desdits deux points d'attache 36 et 36'. De cette manière on évite la création de contraintes dans la paroi concernée, lorsque les points d'attache 36 et 36' s'écartent (ou se rapprochent) l'un de l'autre à cause de la dilatation (ou de la rétractation) du secteur 130.Advantageously, to attach the sector 130 to the walls 26, 28, a fastening system is used which allows the approximation or spacing (in the circumferential direction of the chamber bottom) of said two attachment points 36 and 36 '. In this way the creation of stresses in the wall in question is avoided, when the attachment points 36 and 36 'deviate (or come closer) from one another because of the expansion (or retraction). sector 130.

Un tel système d'attache correspond, par exemple, à un boulon 52 coopérant avec au moins un trou oblong 50 dont la largeur correspond sensiblement au diamètre de la vis du boulon 52. Ce trou oblong 50 peut être ménagé dans un rabat 132 (134) du secteur de fond de chambre 130, dans une paroi 26 (28) ou dans ces deux pièces à la fois. Dans l'exemple, on a choisi de réaliser un trou oblong 50 seulement dans les rabats 132, 134. Les trous réalisés dans les parois 26, 29, sont tous cylindriques, de diamètre correspondant à celui des vis des boulons 52 utilisés.Such an attachment system corresponds, for example, to a bolt 52 cooperating with at least one oblong hole 50 whose width corresponds substantially to the diameter of the screw of the bolt 52. This oblong hole 50 may be formed in a flap 132 (134). ) of the chamber bottom sector 130, in a wall 26 (28) or in these two parts at a time. In the example, it was chosen to make an oblong hole 50 only in the flaps 132, 134. The holes made in the walls 26, 29, are all cylindrical, of diameter corresponding to that of the screws of the bolts 52 used.

Chaque trou oblong 50 est orienté circonférentiellement (i.e. la longueur de chaque trou est orientée, suivant la circonférence du fond de chambre 30 annulaire) et le boulon 52 coopérant avec ce trou 50, peut donc se déplacer circonférentiellement, à l'intérieur du trou 50 comme indiqué par la double flèche B. Dans l'exemple des figures tous les points d'attache 36, 36', sont réalisés par boulonnage mais seul un point de fixation 36' sur deux est réalisé par boulonnage à travers un trou oblong 50. Pour simplifier les figures, tous les boulons 52 ne sont pas représentés.Each oblong hole 50 is circumferentially oriented (ie, the length of each hole is oriented along the circumference of the annular chamber bottom) and the bolt 52 cooperating with this hole 50 can thus move circumferentially within the hole 50 as shown by the double arrow B. In the example of the figures all the attachment points 36, 36 'are made by bolting but only one fixing point 36' out of two is made by bolting through an oblong hole 50. To simplify the figures, all bolts 52 are not shown.

Les secteurs 130 du fond de chambre 30 étant réalisés en matériau métallique, généralement en alliage métallique réfractaire, il est facile de fixer sur ceux-ci, par exemple par soudage (par brasage), les divers éléments d'un système d'injection de carburant 20, comme un système de maintien 19 et un mélangeur 21. Par ailleurs, si nécessaire, il est également possible de fixer sur la paroi aval de chaque secteur 130 un déflecteur 23 visant à protéger ce secteur 130 des gaz à hautes températures de la chambre de combustion. Un tel déflecteur 23 est optionnel et sa présence dépend principalement de la résistance propre, aux hautes températures, du matériau utilisé pour réaliser les segments 130.The sectors 130 of the chamber bottom 30 being made of metal material, generally made of refractory metal alloy, it is easy to fix on them, for example by welding (soldering), the various elements of an injection system. fuel 20, as a holding system 19 and a mixer 21. Furthermore, if necessary, it is also possible to fix on the downstream wall of each sector 130 a baffle 23 for protecting the sector 130 of the high temperature gases of the combustion chamber. Such a deflector 23 is optional and its presence depends mainly on the high temperature resistance of the material used to produce the segments 130.

Claims (9)

Chambre de combustion annulaire (24) d'une turbomachine, comprenant une paroi interne (26), une paroi externe (28) et un fond de chambre (30) disposé entre lesdites parois dans la région amont de ladite chambre, caractérisée en ce que le fond de chambre (30) est divisé en plusieurs secteurs (130), chaque secteur étant attaché auxdites parois (26, 28), et lesdits secteurs (130) présentant des bords latéraux (130a, 130b) tels que les bords latéraux de deux secteurs voisins se chevauchent.Annular combustion chamber (24) of a turbomachine, comprising an inner wall (26), an outer wall (28) and a chamber bottom (30) disposed between said walls in the upstream region of said chamber, characterized in that the chamber floor (30) is divided into several sectors (130), each sector being attached to said walls (26, 28), and said sectors (130) having lateral edges (130a, 130b) such as the side edges of two neighboring sectors overlap. Chambre de combustion selon la revendication 1, caractérisée en ce que chaque secteur (130) comprend une lèvre (60) s'étendant le long d'un de ses bords latéraux (130a), cette lèvre étant en saillie par rapport à l'une des faces de ce secteur et recouvrant le bord latéral (130b) du secteur voisin.Combustion chamber according to claim 1, characterized in that each sector (130) comprises a lip (60) extending along one of its lateral edges (130a), this lip being projecting with respect to one faces of this sector and covering the lateral edge (130b) of the neighboring sector. Chambre de combustion selon la revendication 2, caractérisée en ce que chaque secteur (130) présente une partie centrale (133) prolongée par deux rabats (132, 134) attachés respectivement auxdites parois interne (26) et externe (28), ladite lèvre (60) s'étendant sensiblement sur toute la longueur de la partie centrale (133).Combustion chamber according to claim 2, characterized in that each sector (130) has a central portion (133) extended by two flaps (132, 134) respectively attached to said inner (26) and outer (28) walls, said lip ( 60) extending substantially the entire length of the central portion (133). Chambre de combustion selon l'une quelconque des revendications 1 à 3, caractérisée en ce que chaque secteur (130) est attaché à au moins une paroi (26, 28) en deux points d'attache (36, 36').Combustion chamber according to any one of claims 1 to 3, characterized in that each sector (130) is attached to at least one wall (26, 28) at two attachment points (36, 36 '). Chambre de combustion selon la revendication 4, caractérisée en ce qu'elle comprend un système d'attache dudit secteur (130) à ladite au moins une paroi (26, 28), qui autorise le rapprochement ou l'écartement desdits deux points d'attache (36, 36').Combustion chamber according to claim 4, characterized in that it comprises a fastening system of said sector (130) to said at least one wall (26, 28), which allows the approximation or the spacing of said two points of fastener (36, 36 '). Chambre de combustion selon la revendication 5, caractérisée en ce que ledit système d'attache correspond à une attache par boulonnage à travers au moins un trou oblong (50).Combustion chamber according to claim 5, characterized in that said fastening system corresponds to a fastening by bolting through at least one oblong hole (50). Chambre de combustion selon l'une quelconque des revendications 1 à 6, caractérisée en ce que le fond de chambre (30) est en métal ou en alliage métallique, tandis que les parois (26, 28) sont en matériau céramique.Combustion chamber according to any one of claims 1 to 6, characterized in that the chamber base (30) is made of metal or metal alloy, while the walls (26, 28) are made of ceramic material. Chambre de combustion selon l'une quelconque des revendications 1 à 7, caractérisée en ce que chaque secteur (130) du fond de chambre (30) est équipé d'un déflecteur (23).Combustion chamber according to any one of claims 1 to 7, characterized in that each sector (130) of the chamber bottom (30) is equipped with a deflector (23). Turbomachine comprenant une chambre de combustion (24) selon l'une quelconque des revendications précédentes.A turbomachine comprising a combustion chamber (24) according to any one of the preceding claims.
EP07101934A 2006-02-10 2007-02-08 Annular combustion chamber of a turbomachine Active EP1818615B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650473A FR2897417A1 (en) 2006-02-10 2006-02-10 ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE

Publications (2)

Publication Number Publication Date
EP1818615A1 true EP1818615A1 (en) 2007-08-15
EP1818615B1 EP1818615B1 (en) 2008-08-13

Family

ID=37102075

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07101934A Active EP1818615B1 (en) 2006-02-10 2007-02-08 Annular combustion chamber of a turbomachine

Country Status (8)

Country Link
US (1) US7770398B2 (en)
EP (1) EP1818615B1 (en)
JP (1) JP2007212130A (en)
CN (1) CN101017001A (en)
CA (1) CA2577514C (en)
DE (1) DE602007000064D1 (en)
FR (1) FR2897417A1 (en)
RU (1) RU2435107C2 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2040001A2 (en) * 2007-09-21 2009-03-25 Snecma Annular combustion chamber for a gas turbine engine
FR2930628A1 (en) * 2008-04-24 2009-10-30 Snecma Sa ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE
EP2463583A1 (en) * 2010-12-06 2012-06-13 Alstom Technology Ltd Gas turbine and method for reconditioning such a gas turbine
EP2503246A3 (en) * 2011-03-22 2014-11-26 Rolls-Royce Deutschland Ltd & Co KG Segmented combustion chamber head
FR3078384A1 (en) * 2018-02-28 2019-08-30 Safran Aircraft Engines DOUBLE BOTTOM CHAMBER COMBUSTION CHAMBER
EP3858606A1 (en) 2020-01-28 2021-08-04 (CNBM) Bengbu Design & Research Institute for Glass Industry Co., Ltd. Coloured façade element with composite panel structure
EP3859795A1 (en) 2020-01-28 2021-08-04 (CNBM) Bengbu Design & Research Institute for Glass Industry Co., Ltd. Coloured plate-shaped component with structured cover plate and colour filter layer

Families Citing this family (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7578134B2 (en) * 2006-01-11 2009-08-25 General Electric Company Methods and apparatus for assembling gas turbine engines
FR2903171B1 (en) * 2006-06-29 2008-10-17 Snecma Sa CRABOT LINK ARRANGEMENT FOR TURBOMACHINE COMBUSTION CHAMBER
FR2909748B1 (en) * 2006-12-07 2009-07-10 Snecma Sa BOTTOM BOTTOM, METHOD OF MAKING SAME, COMBUSTION CHAMBER COMPRISING SAME, AND TURBOJET ENGINE
FR2910115B1 (en) * 2006-12-19 2012-11-16 Snecma DEFLECTOR FOR BOTTOM OF COMBUSTION CHAMBER, COMBUSTION CHAMBER WHERE IT IS EQUIPPED AND TURBOREACTOR COMPRISING THEM
FR2914399B1 (en) * 2007-03-27 2009-10-02 Snecma Sa FURNITURE FOR BOTTOM OF COMBUSTION CHAMBER.
FR2918444B1 (en) * 2007-07-05 2013-06-28 Snecma CHAMBER BOTTOM DEFLECTOR, COMBUSTION CHAMBER COMPRISING SAME, AND GAS TURBINE ENGINE WHERE IT IS EQUIPPED
FR2918443B1 (en) * 2007-07-04 2009-10-30 Snecma Sa COMBUSTION CHAMBER COMPRISING THERMAL PROTECTION DEFLECTORS OF BOTTOM BOTTOM AND GAS TURBINE ENGINE BEING EQUIPPED
FR2929689B1 (en) * 2008-04-03 2013-04-12 Snecma Propulsion Solide GAS TURBINE COMBUSTION CHAMBER WITH SECTORIZED INTERNAL AND EXTERNAL WALLS
FR2929690B1 (en) * 2008-04-03 2012-08-17 Snecma Propulsion Solide COMBUSTION CHAMBER SECTORIZED IN CMC FOR GAS TURBINE
US8266914B2 (en) * 2008-10-22 2012-09-18 Pratt & Whitney Canada Corp. Heat shield sealing for gas turbine engine combustor
FR2964725B1 (en) * 2010-09-14 2012-10-12 Snecma AERODYNAMIC FAIRING FOR BOTTOM OF COMBUSTION CHAMBER
FR2982010B1 (en) * 2011-10-26 2013-11-08 Snecma ANNULAR COMBUSTION CHAMBER IN A TURBOMACHINE
CN103486619B (en) * 2012-06-13 2016-02-24 中国航空工业集团公司沈阳发动机设计研究所 A kind of burner inner liner fixed structure
CN103868095B (en) * 2012-12-14 2016-05-04 中航商用航空发动机有限责任公司 Active flow control and regulation device and the engine chamber that comprises this device
EP3030771B8 (en) 2013-08-05 2021-04-07 Raytheon Technologies Corporation Diffuser case mixing chamber for a turbine engine
US8984896B2 (en) * 2013-08-23 2015-03-24 Pratt & Whitney Canada Corp. Interlocking combustor heat shield panels
US9534784B2 (en) 2013-08-23 2017-01-03 Pratt & Whitney Canada Corp. Asymmetric combustor heat shield panels
FR3011620B1 (en) * 2013-10-04 2018-03-09 Snecma TURBOMACHINE COMBUSTION CHAMBER WITH IMPROVED AIR INPUT PASSING DOWN A CANDLE PITCH ORIFICE
EP3066390B1 (en) 2013-11-04 2020-10-21 United Technologies Corporation Gas turbine engine wall assembly with offset rail
US10240790B2 (en) 2013-11-04 2019-03-26 United Technologies Corporation Turbine engine combustor heat shield with multi-height rails
EP3084310A4 (en) 2013-12-19 2017-01-04 United Technologies Corporation Gas turbine engine wall assembly with circumferential rail stud architecture
WO2015103357A1 (en) 2013-12-31 2015-07-09 United Technologies Corporation Gas turbine engine wall assembly with enhanced flow architecture
GB201408690D0 (en) 2014-05-16 2014-07-02 Rolls Royce Plc A combustion chamber arrangement
US10648669B2 (en) 2015-08-21 2020-05-12 Rolls-Royce Corporation Case and liner arrangement for a combustor
US10669939B2 (en) 2016-10-26 2020-06-02 Raytheon Technologies Corporation Combustor seal for a gas turbine engine combustor
US10670269B2 (en) 2016-10-26 2020-06-02 Raytheon Technologies Corporation Cast combustor liner panel gating feature for a gas turbine engine combustor
US10823410B2 (en) 2016-10-26 2020-11-03 Raytheon Technologies Corporation Cast combustor liner panel radius for gas turbine engine combustor
US10830448B2 (en) 2016-10-26 2020-11-10 Raytheon Technologies Corporation Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
US10935243B2 (en) 2016-11-30 2021-03-02 Raytheon Technologies Corporation Regulated combustor liner panel for a gas turbine engine combustor
US10739001B2 (en) 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
FR3084446B1 (en) * 2018-07-25 2024-02-02 Safran Aircraft Engines MONOBLOCK COMBUSTION CHAMBER
CN109340821B (en) * 2018-10-16 2020-09-08 安徽省飞腾航空科技有限公司 Light aero-engine combustion chamber structure and working mode thereof
US11143108B2 (en) * 2019-03-07 2021-10-12 Pratt & Whitney Canada Corp. Annular heat shield assembly for combustor
FR3107106B1 (en) * 2020-02-11 2022-07-08 Safran Aircraft Engines Assembly COMPRISING a crankcase and a combustion chamber, and turbomachine so equipped

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2431096A1 (en) * 1978-08-14 1980-02-08 Gen Electric COMBUSTION CHAMBER DOME OF A GAS TURBINE ENGINE
EP0724119A2 (en) * 1995-01-26 1996-07-31 General Electric Company Dome assembly for a gas turbine engine
US6513330B1 (en) * 2000-11-08 2003-02-04 Allison Advanced Development Company Diffuser for a gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
GB2295887A (en) * 1994-12-08 1996-06-12 Rolls Royce Plc Combustor assembly
US6557349B1 (en) * 2000-04-17 2003-05-06 General Electric Company Method and apparatus for increasing heat transfer from combustors
FR2825779B1 (en) * 2001-06-06 2003-08-29 Snecma Moteurs COMBUSTION CHAMBER EQUIPPED WITH A CHAMBER BOTTOM FIXING SYSTEM

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2431096A1 (en) * 1978-08-14 1980-02-08 Gen Electric COMBUSTION CHAMBER DOME OF A GAS TURBINE ENGINE
EP0724119A2 (en) * 1995-01-26 1996-07-31 General Electric Company Dome assembly for a gas turbine engine
US6513330B1 (en) * 2000-11-08 2003-02-04 Allison Advanced Development Company Diffuser for a gas turbine engine

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2485405C2 (en) * 2007-09-21 2013-06-20 Снекма Circular combustion chamber of gas turbine engine
EP2040001A2 (en) * 2007-09-21 2009-03-25 Snecma Annular combustion chamber for a gas turbine engine
EP2040001A3 (en) * 2007-09-21 2010-02-17 Snecma Annular combustion chamber for a gas turbine engine
US8156744B2 (en) 2007-09-21 2012-04-17 Snecma Annular combustion chamber for a gas turbine engine
FR2921462A1 (en) * 2007-09-21 2009-03-27 Snecma Sa ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
WO2009133322A1 (en) * 2008-04-24 2009-11-05 Snecma Annular combustion chamber for a turbomachine
FR2930628A1 (en) * 2008-04-24 2009-10-30 Snecma Sa ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE
EP2463583A1 (en) * 2010-12-06 2012-06-13 Alstom Technology Ltd Gas turbine and method for reconditioning such a gas turbine
CH704185A1 (en) * 2010-12-06 2012-06-15 Alstom Technology Ltd GAS TURBINE AND METHOD FOR recondition SUCH GAS TURBINE.
AU2011253595B2 (en) * 2010-12-06 2015-07-16 General Electric Technology Gmbh Gas turbine and method for reconditioning such a gas turbine
EP2503246A3 (en) * 2011-03-22 2014-11-26 Rolls-Royce Deutschland Ltd & Co KG Segmented combustion chamber head
US9328926B2 (en) 2011-03-22 2016-05-03 Rolls-Royce Deutschland Ltd & Co Kg Segmented combustion chamber head
US11248793B2 (en) 2018-02-28 2022-02-15 Safran Aircraft Engines Combustion chamber having a double chamber bottom
WO2019166745A1 (en) * 2018-02-28 2019-09-06 Safran Aircraft Engines Combustion chamber having a double chamber bottom
FR3078384A1 (en) * 2018-02-28 2019-08-30 Safran Aircraft Engines DOUBLE BOTTOM CHAMBER COMBUSTION CHAMBER
EP3858606A1 (en) 2020-01-28 2021-08-04 (CNBM) Bengbu Design & Research Institute for Glass Industry Co., Ltd. Coloured façade element with composite panel structure
EP3859795A1 (en) 2020-01-28 2021-08-04 (CNBM) Bengbu Design & Research Institute for Glass Industry Co., Ltd. Coloured plate-shaped component with structured cover plate and colour filter layer
WO2021151374A1 (en) 2020-01-28 2021-08-05 (Cnbm) Bengbu Design & Research Institute For Glass Industry Co., Ltd Colored plate-shaped component with structured cover plate and color filter layer
WO2021151373A1 (en) 2020-01-28 2021-08-05 (Cnbm) Bengbu Design & Research Institute For Glass Industry Co., Ltd Colored facade element with composite pane structure

Also Published As

Publication number Publication date
RU2007105074A (en) 2008-08-20
CA2577514A1 (en) 2007-08-10
FR2897417A1 (en) 2007-08-17
US7770398B2 (en) 2010-08-10
EP1818615B1 (en) 2008-08-13
CN101017001A (en) 2007-08-15
JP2007212130A (en) 2007-08-23
US20070186558A1 (en) 2007-08-16
DE602007000064D1 (en) 2008-09-25
CA2577514C (en) 2015-08-11
RU2435107C2 (en) 2011-11-27

Similar Documents

Publication Publication Date Title
EP1818615B1 (en) Annular combustion chamber of a turbomachine
CA2577520C (en) Annular combustion chamber of turbine engine
EP2334909B1 (en) Sealing between a combustion chamber and a turbine distributor in a turbine engine
EP1734305B1 (en) Assembly of an annular combustion chamber for a turbine
EP3833861B1 (en) Exhaust cone with flexible attachment
EP2142787B1 (en) Dual flow gas turbine comprising an exhaust system
CA2469849C (en) Combustion chamber having a flexible liaison between the chamber floor and chamber wall
EP1265030B1 (en) Mounting of a ceramic matrix composite combustion chamber with flexible shrouds
EP1265035B1 (en) Double mounting of a ceramic matrix composite combustion chamber
EP1265033B1 (en) Combustion chamber with a system for mounting the chamber end wall
EP1265036A1 (en) Elastic mounting of a ceramic matrix composite combustion chamber inside a metallic casing
EP1557553A1 (en) Monobloc arm for a postcombustion device of a double flow turboengine
EP1265032A1 (en) Ceramic matrix composite material gas turbine combustion chamber
CA2598543A1 (en) Annular combustion chamber of a turbomachine
FR3004518A1 (en) ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE
WO2019202234A1 (en) Turbine ring assembly with inter-sector sealing
FR2896575A1 (en) Annular combustion chamber for e.g. turbo propeller, has chamber base arranged between inner and outer walls in region that is provided upstream to chamber, where chamber base and walls are made of ceramic material
FR2825778A1 (en) Coupling between fuel injector nozzle and turbine combustion chamber base has metal mixer/deflector assembly sliding in composition base aperture
FR3017928B1 (en) TURBOMACHINE WITH EXTERNAL FLANGE OF "SANDWICH" COMBUSTION CHAMBER
FR2825782A1 (en) Turbine with metal casing has composition combustion chamber fitted with sliding coupling to allow for differences in expansion coefficients
FR2943404A1 (en) Annular combustion chamber for turbine engine e.g. turbojet engine, of aircraft, has chamber base providing fixing edge fixed at annular wall, and air pipe flange provided with base and projecting toward downstream from base
FR3129988A1 (en) COMBUSTION GAS EXHAUST PIPE FOR AN AIRCRAFT TURBOMACHINE
FR3129987A1 (en) COMBUSTION GAS EXHAUST PIPE FOR AN AIRCRAFT TURBOMACHINE
EP4146913A1 (en) Improved cmc guide vane for a turbomachine turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20070208

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

RIN1 Information on inventor provided before grant (corrected)

Inventor name: DE SOUSA, MARIO

Inventor name: NOEL, THOMAS

Inventor name: HERNANDEZ, DIDIER

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

AKX Designation fees paid

Designated state(s): DE FR GB IT

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 602007000064

Country of ref document: DE

Date of ref document: 20080925

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20090514

PGRI Patent reinstated in contracting state [announced from national office to epo]

Ref country code: IT

Effective date: 20110501

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 602007000064

Country of ref document: DE

Representative=s name: CBDL PATENTANWAELTE GBR, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230119

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230120

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240123

Year of fee payment: 18

Ref country code: GB

Payment date: 20240123

Year of fee payment: 18